Newtonian flow over a stationary body in unsteady flow.

Abstract

The equations governing either two-dimensional or axisymmetric, unsteady hypersonic flow over a stationary body are developed on the hypothesis of a thin shock layer. These approximate equations are integrated to obtain a formal generalization of the NewtonBusemann formula for the pressure on the body. It is found that, just as in steady flow, tangential velocity, mass flux, and entropy are conserved by fluid particles within the shock layer; however, retarded-time effects render specific applications more complicated.